[Federal Register: December 7, 2006 (Volume 71, Number 235)]
[Rules and Regulations]
[Page 70865-70868]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07de06-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25423; Directorate Identifier 2006-NM-029-AD;
Amendment 39-14845; AD 2006-25-04]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to all Airbus Model A300 airplanes. That AD
currently requires repetitive inspections for cracking and corrosion in
the lower rim area of the rear pressure bulkhead and adjacent areas,
repetitive inspections for cracking or corrosion in the service
apertures and the upper rim area of the rear pressure bulkhead, and
corrective actions if necessary. This new AD removes certain repetitive
inspections and reduces the repetitive interval of one inspection. This
new AD also requires an inspection for missing or damaged sealant in
the area between the outer attachment angle and circumferential joint
doubler, and corrective action if necessary. This new AD also requires
additional inspections for corrosion of certain areas and repetitive
inspections for airplanes on which repairs have been done. This AD
results from reports of corrosion and cracking in the various
components associated with the rear pressure bulkhead. We are issuing
this AD to prevent reduced structural capability of the fuselage and
consequent decompression of the airplane.
DATES: This AD becomes effective January 11, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of January 11,
2007.
ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov
or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Thomas Stafford, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at http://dms.dot.gov or in person at the Docket Management
Facility office between 9 am and 5 pm, Monday through Friday, except
Federal holidays. The Docket Management Facility office (telephone
(800) 647-5227) is located on the plaza level of the Nassif Building at
the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 90-03-08, amendment 39-
6481 (55 FR 1799, January 19, 1990). The existing AD applies to all
Airbus Model A300 series airplanes. That NPRM was published in the
Federal Register on August 1, 2006 (71 FR 43386). That NPRM proposed to
continue to require repetitive inspections for cracking and corrosion
in the lower rim area of the rear pressure bulkhead and adjacent areas,
repetitive inspections for cracking or corrosion in the service
apertures and the upper rim area of the rear pressure bulkhead, and
corrective actions if necessary. That NPRM also proposed to remove
certain repetitive inspections and reduce the repetitive interval of
one inspection. That NPRM also proposed to require an inspection for
missing or damaged sealant in the area between the outer attachment
angle and circumferential joint doubler, and corrective action if
necessary. That NPRM also proposed to require additional inspections
for corrosion of certain areas and repetitive inspections for airplanes
on which repairs have been done.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.
Request To Refer to Latest Issue of the Service Bulletin and Revise
Compliance Time
Airbus requests that Service Bulletin A300-53-0218, Revision 03,
dated August 3, 2006, be referenced in the NPRM. (Airbus Service
Bulletin A300-53-0218, Revision 02, dated May 10, 2005, was referenced
as the appropriate source of service information for doing the actions
specified in the NPRM.) Airbus also states that the compliance time for
doing the repetitive sealant inspection has been revised from 6,000
landings to 8,000 landings to match the compliance times specified in
French airworthiness directive F-2005-093 R1, dated August 3, 2005
(which was referenced in the NPRM as the related French airworthiness
directive).
We agree with the commenter to refer to Revision 03 of the service
bulletin. Revision 03 of the service bulletin contains essentially the
same procedures as Revision 02 of the service bulletin for doing the
actions specified the NPRM. We have revised the final rule accordingly.
We have also added paragraph (o) of the final rule to allow actions
done before the effective date of this AD in accordance with Revision
02 of the service bulletin to be acceptable for compliance.
We also agree to revise the compliance time of the repetitive
sealant inspection. The French airworthiness directive specifies that
the repetitive interval is 8,000 landings for the upper part of rear
pressure bulkhead surrounding area. The sealant inspection is done on
the aft face of the rear pressure bulkhead. Therefore we have revised
paragraph (i) of this final rule accordingly.
Request To Change Incorporation of Certain Information
The Modification and Replacement Parts Association (MARPA) states
that, typically, airworthiness directives are based on service
information originating with the type certificate holder or its
suppliers. MARPA adds that manufacturer service documents are privately
authored instruments generally having copyright protection against
duplication and distribution. MARPA notes that when a service document
is incorporated by reference into a public document, such as an
airworthiness directive, it loses its private, protected status and
becomes a public document. MARPA adds that if a service document is
used as a mandatory element of compliance, it should not simply be
referenced, but should be incorporated into the regulatory document; by
definition,
[[Page 70866]]
public laws must be public, which means they cannot rely upon private
writings.
MARPA adds that incorporated by reference service documents should
be made available to the public by publication in the Docket Management
System (DMS), keyed to the action that incorporates them. MARPA notes
that the stated purpose of the incorporation by reference method is
brevity, to keep from expanding the Federal Register needlessly by
publishing documents already in the hands of the affected individuals;
traditionally, ``affected individuals'' means aircraft owners and
operators, who are generally provided service information by the
manufacturer. MARPA adds that a new class of affected individuals has
emerged, since the majority of aircraft maintenance is now performed by
specialty shops instead of aircraft owners and operators. MARPA notes
that this new class includes maintenance and repair organizations,
component servicing and repair shops, parts purveyors and distributors,
and organizations manufacturing or servicing alternatively certified
parts under section 21.303 (``Replacement and modification parts'') of
the Federal Aviation Regulations (14 CFR 21.303). MARPA adds that the
concept of brevity is now nearly archaic as documents exist more
frequently in electronic format than on paper. Therefore, MARPA asks
that the service documents deemed essential to the accomplishment of
the NPRM be incorporated by reference into the regulatory instrument
and published in the DMS.
We do not agree that documents should be incorporated by reference
during the NPRM phase of rulemaking. The Office of the Federal Register
(OFR) requires that documents that are necessary to accomplish the
requirements of the AD be incorporated by reference during the final
rule phase of rulemaking. This final rule incorporates by reference the
documents necessary for the accomplishment of the requirements mandated
by this AD. Further, we point out that while documents that are
incorporated by reference do become public information, they do not
lose their copyright protection. For that reason, we advise the public
to contact the manufacturer to obtain copies of the referenced service
information.
In regard to the commenter's request to post service bulletins on
the Department of Transportation's DMS, we are currently in the process
of reviewing issues surrounding the posting of service bulletins on the
DMS as part of an AD docket. Once we have thoroughly examined all
aspects of this issue and have made a final determination, we will
consider whether our current practice needs to be revised. No change to
the final rule is necessary in response to this comment.
Clarification of Requirements of Paragraph (f)(2) of the Final Rule
We have added the phrase ``as applicable'' to paragraph (f)(2) of
the final rule to clarify that the actions specified in paragraph
(f)(2)(i) and (f)(2)(ii) of the final rule are required to be done only
for the applicable airplanes identified in paragraphs (f)(2)(i) and
(f)(2)(ii) of the final rule. We have also added the word ``inclusive''
to the range of manufacturer serial numbers specified in paragraphs
(f)(2)(i) and (f)(2)(ii) of the final rule in order to clarify the
range of the applicable airplanes.
Clarification of Reference in Paragraph (h)(5) of the Final Rule
We made a typographical error in paragraph (h)(5) of the NPRM when
we referred to paragraphs (g)(5)(i) and (g)(5)(ii). The correct
paragraph reference is (h)(5)(i) and (h)(5)(ii). We have revised
paragraph (h)(5) of the final rule accordingly.
Conclusion
We have carefully reviewed the available data, including the
comments that have been received, and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this AD.
Estimated Costs
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Number of
Work Average U.S.-
Action hours labor rate Cost per airplane registered Fleet cost
per hour airplanes
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Inspections (required by AD 90- 10 $80 $800, per inspection cycle................ 51 $40,800, per inspection cycle.
03-08).
New Inspections (required by 10 80 $800, per inspection cycle................ 51 $40,800, per inspection cycle.
this AD).
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the National Government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
[[Page 70867]]
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-6481 (55 FR 1799, January 19, 1990) and by adding
the following new airworthiness directive (AD):
2006-25-04 Airbus: Amendment 39-14845. Docket No. FAA-2006-25423;
Directorate Identifier 2006-NM-029-AD.
Effective Date
(a) This AD becomes effective January 11, 2007.
Affected ADs
(b) This AD supersedes AD 90-03-08.
Applicability
(c) This AD applies to all Airbus Model A300 airplanes,
certificated in any category; except the following airplanes:
(1) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes;
(2) Model A300 B4-605R and B4-622R airplanes;
(3) Model A300 F4-605R and F4-622R airplanes; and
(4) Model A300 C4-605R Variant F airplanes.
Unsafe Condition
(d) This AD results from reports of corrosion and cracking in
the various components associated with the rear pressure bulkhead.
We are issuing this AD to prevent reduced structural capability of
the fuselage and consequent decompression of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Certain Requirements of Ad 90-03-08 With New Repetitive
Intervals
Initial Inspections
(f) Within the time limits specified in paragraph (g) of this
AD, conduct the inspections specified in paragraphs (f)(1) through
(f)(4) of this AD in accordance with Airbus Service Bulletin A300-
53-218, Revision 1, dated July 28, 1989; or Airbus Service Bulletin
A300-53-0218, Revision 03, dated August 3, 2006. After the effective
date of this AD, Airbus Service Bulletin A300-53-0218, Revision 03,
dated August 3, 2006, must be used.
(1) Perform a detailed inspection for corrosion and cracking of
the upper rim area of the rear pressure bulkhead from the aft face.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
(2) Perform an eddy current inspection for cracks from the
outboard side in the applicable areas specified in paragraph
(f)(2)(i) or (f)(2)(ii) of this AD, as applicable.
(i) For airplanes, manufacturer's serial number (MSN) 003
through 008 inclusive: Between Stringer (STGR) 25 left hand (LH) and
right hand (RH).
(ii) For airplanes, MSN 019 through 305 inclusive: Between STGR
26 LH and RH.
(3) Perform a detailed inspection for cracks and corrosion of
the service apertures in the rear pressure bulkhead.
(4) Perform an eddy current inspection for cracks of the
apertures for the auxiliary power unit (APU) bleed-air and fuel.
(g) At the applicable time specified in paragraph (g)(1) or
(g)(2) of this AD, do the inspections required by paragraph (f) of
this AD.
(1) For airplanes having accumulated 26,000 landings or fewer as
of February 23, 1990 (the effective date of AD 90-03-08): Perform
the initial inspections required by paragraph (f) of this AD, prior
to the accumulation of 24,000 landings or within 2,000 landings
after February 23, 1990, whichever occurs later.
(2) For airplanes having accumulated more than 26,000 landings
as of February 23, 1990: Perform the initial inspections required by
paragraph (f) of this AD, within 1,000 landings after February 23,
1990.
Repetitive Inspections
(h) If no cracking or corrosion is found during the inspections
required by paragraph (f) of this AD, repeat the inspections
specified in paragraphs (h)(1), (h)(2), (h)(3), (h)(4), and (h)(5)
of this AD thereafter at the times specified in the paragraphs.
(1) Repeat the detailed inspections of the upper rim area
specified in paragraph (f)(1) of this AD thereafter at intervals not
to exceed 8,000 landings.
(2) Repeat the eddy current inspection from the outboard side
between STGR 25 LH and RH, or STGR 26 LH and RH, as applicable,
specified in paragraph (f)(2) of this AD thereafter at intervals not
to exceed 8,000 landings.
(3) Repeat the detailed inspection of the service apertures
specified in paragraph (f)(3) of this AD thereafter at intervals not
to exceed 6,000 landings.
(4) Repeat eddy current inspections of APU fuel apertures
specified in paragraph (f)(4) of this AD thereafter at intervals not
to exceed 6,000 landings.
(5) At the earlier of the times specified in paragraphs
(h)(5)(i) and (h)(5)(ii) of this AD, do the eddy current inspection
of the APU bleed-air line service aperture specified in paragraph
(f)(4) of this AD. Repeat the inspection thereafter at intervals not
to exceed 6,000 landing.
(i) Within 12,000 landings since the last inspection of the APU
bleed-air line service aperture specified in paragraph (f)(4) of
this AD.
(ii) Within 6,000 landings since the last inspection of the APU
bleed-air line service aperture specified in paragraph (f)(4) of
this AD or within 2,000 landings after the effective date of this
AD, whichever occurs later.
New Requirements of This AD
Inspection for Sealant and Corrective Action
(i) Within the time limits specified in paragraph (j) of this
AD: Do a general visual inspection of the area between the outer
attachment angle and circumferential joint doubler to determine if
sealant is missing or damaged and do all applicable corrective
actions, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-53-0218, Revision 03, dated August 3,
2006. Do all applicable corrective actions before further flight.
Repeat the inspection thereafter at intervals not to exceed 8,000
landings.
Note 2: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''
(j) At the applicable time specified in paragraph (j)(1) or
(j)(2) of this AD, do the inspections required by paragraph (i) of
this AD.
(1) For airplanes having accumulated 26,000 landings or fewer as
of the effective date of this AD: Perform the initial inspection
required by paragraph (i) of this AD prior to the accumulation of
24,000 landings, or within 2,000 landings after the effective date
of this AD, whichever occurs later.
(2) For airplanes having accumulated more than 26,000 landings
as of the effective date
[[Page 70868]]
of this AD: Perform the initial inspection required by paragraph (i)
of this AD within 1,000 landings after the effective date of this
AD.
Additional Inspections
(k) For airplanes on which the inspections specified in
paragraphs (f)(2), (f)(4), (h)(2), and (h)(4) of this AD are
accomplished after the effective date of this AD: Where this AD
requires an eddy current inspection for cracks, do a detailed
inspection for corrosion at the same time as the eddy current
inspection for cracks, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-0218, Revision 03,
dated August 3, 2006.
(l) For airplanes on which the inspections specified in
paragraphs (f)(2) and (h)(2) of this AD are accomplished after the
effective date of this AD: If any crack is found during any
inspection required by paragraph (f)(2) or (h)(2), before further
flight, do an X-ray inspection for cracking of the rim area of the
rear pressure bulkhead in the area of STGR 21 LH and RH in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-53-0218, Revision 03, dated August 3, 2006.
New Repetitive Inspections
(m) For airplanes on which a repair has been done in accordance
with Airbus Service Bulletin A300-53-218, Revision 1, dated July 28,
1989; Airbus Service Bulletin A300-53-0218, Revision 02, dated May
10, 2005; or Revision 03, dated August 3, 2006; before the effective
date of this AD: At the later of the times specified in paragraphs
(m)(1) and (m)(2) of this AD, do the inspections specified in
paragraphs (h), (k), and (l) of this AD. Repeat the inspections
specified in paragraphs (h), (k), and (l) of this AD thereafter at
the applicable times specified in paragraph (h) of this AD.
(1) Within the times specified in paragraph (h) of this AD.
(2) Within 2,000 landings after the effective date of this AD.
Corrective Actions for Cracking and Corrosion and Repetitive
Inspections
(n) If cracking or corrosion is found during any inspection
required by paragraph (f), (h), (k), (l) or (m) of this AD, repair
prior to further flight, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-218, Revision 1,
dated July 28, 1989; or Airbus Service Bulletin A300-53-0218,
Revision 03, dated August 3, 2006. As of the effective date of this
AD, do the repair in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A300-53-0218, Revision 03, dated August
3, 2006; except where the service bulletin specifies to contact the
manufacturer to repair certain conditions, this AD requires
repairing those conditions using a method approved by either the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA) (or
its delegated agent). As of the effective date of this AD, repeat
the inspections specified in paragraphs (h), (k), and (l) of this AD
thereafter at the applicable times specified in paragraph (h) of
this AD.
Actions Accomplished According to Previous Issue of Service
Bulletin
(o) Actions accomplished before the effective date of this AD in
accordance with Airbus Service Bulletin A300-53-0218, Revision 02,
dated May 10, 2005, are considered acceptable for compliance with
the corresponding actions specified in this AD.
Alternative Methods of Compliance (AMOCs)
(p)(1) The Manager, International Branch, ANM-116, has the
authority to approve AMOCs for this AD, if requested in accordance
with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) AMOCs approved previously in accordance with AD 90-03-08 are
not approved as AMOCs with this AD.
Related Information
(q) French airworthiness directive F-2005-093 R1, dated August
3, 2005, also addresses the subject of this AD.
Material Incorporated by Reference
(r) You must use Airbus Service Bulletin A300-53-218, Revision
1, dated July 28, 1989; and Airbus Service Bulletin A300-53-0218,
Revision 03, dated August 3, 2006; as applicable; to perform the
actions that are required by this AD, unless the AD specifies
otherwise. Airbus Service Bulletin A300-53-218, Revision 1, dated
July 28, 1989, contains the following effective pages:
------------------------------------------------------------------------
Revision level
Page Nos. shown on page Date shown on page
------------------------------------------------------------------------
1-4, 7, 8, 16, 19-25......... Revision 1..... July 28, 1989.
5, 6, 9-15, 17, 18........... Original....... February 20, 1989.
------------------------------------------------------------------------
The Director of the Federal Register approved the incorporation by
reference of these documents in accordance with 5 U.S.C. 552(a) and
1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France, for a copy of this service information. You
may review copies at the Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif
Building, Washington, DC; on the Internet at http://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Issued in Renton, Washington, on November 20, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-20616 Filed 12-6-06; 8:45 am]
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